Dave, the only real reason to do this now would be to get around the need to design a large rotor system. Even then MI-26 proves this is achievable. The biggest problem is the need for the MGB to handle a growth factor squared to the MUAW, while everything else is linear. This is due to the need to keep tip speeds below ~200 m/s, and handle same power so torque goes up.
Originally Posted by Nick Lappos
It is a pickle that the tilt rotor folks solved using extremely stiff wings with composite materials. Most likely, these dynamic interactions created a real flight envelope problem that hampered the ability to put the aircraft into use. It is possible that modern computation could help the control system, and modern composite materials could help the stiffness.
Chinook LCT is an interesting example of the possibilities, although not used to overcome dynamic problems (from comments made here about Noth Sea ops maybe it should be). For something this big i imagine the rotor collective response time would be less than the stuctural period. The collective could trim to cancel out vertical accelerometer signals near hub, mixed in with pilot input. The whole thing starts to say FBW, which the MI-26 now is...